Abstract:
PROBLEM TO BE SOLVED: To provide a method for efficiently cooling the stator vane of a rotating machine. SOLUTION: In this method for cooling a rotating machine having platforms of adjacent stator vanes 46a, 46b respectively including in their tailing edge regions a meandered channel for cooling the platforms, cooling fluid is introduced to a backmost final leg part in the channel and is introduced to the lateral direction of the backmost leg part, from whose direction a cooling fluid stream is formed including at least 30% of a flow which is led to flow into the channel and is collided with the negative pressure side surfaces 136a, 136b of the adjacent vanes.
Abstract:
PROBLEM TO BE SOLVED: To provide a comparatively simple cooling flow passage for rear end area of a stator vane. SOLUTION: A platform for the stator vane includes a meandering flow passage 168 for cooling fluid including two paths 169, 170 provided in the rear end area of the vane. The meandering flow passage 168 extends to a side, folds back and makes flow flowing backward. An endmost part of the meandering flow passage 168 is adjacent to the rear end 134 so as to accept at least the half flow flowing into the flow passage 168 and to discharge the flow through a gas flow passage surface and the rear end 134 of the platform.
Abstract:
A compressor (22) for a turbine engine (10) includes an inflatable bleed valve (57) that selectively bleeds core airflow from the compressor. The bleed valve has an inlet (58) leading from the compressor and a passageway (112) leading from the inlet. An inflatable valve (116) selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve .
Abstract:
A fan-turbine rotor assembly (24) includes a diffuser (114) mountable to the outer periphery of a multitude of hollow fan blade sections (72) to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. The diffuser includes a fan blade tip shroud inner portion (136) which forms a planar ring about the multiple of fan blade sections. Diffuser support rings (115a, 115b) are mounted to the fan blade tip shroud to further share the radial load applied to the fan blade sections by the blade mounted diffuser and annular turbine (32).
Abstract:
A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.
Abstract:
Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially thereform. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
Abstract:
A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.
Abstract:
A tip turbine engine assembly includes an integral engine outer case (8) located radially outward from a fan assembly (30). The integral outer case (8) includes a rear portion (124) and a forward portion (128) with an arcuate portion (130) that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment (132). Fan inlet guide vanes (22) are integrally formed with the arcuate portion (130) to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally formed in a casting process.